XFOIL Version 6.96 Calculated polar for: BOEING-VERTOL VR-11X AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5133 0.09461 0.09140 -0.0334 1.0000 0.0397 -8.500 -0.5356 0.09238 0.08916 -0.0308 1.0000 0.0397 -8.250 -0.5571 0.08960 0.08632 -0.0289 1.0000 0.0398 -8.000 -0.5729 0.08616 0.08272 -0.0282 0.9991 0.0399 -7.750 -0.5703 0.08102 0.07773 -0.0266 0.9991 0.0406 -7.500 -0.5676 0.07874 0.07552 -0.0239 0.9992 0.0412 -7.250 -0.5707 0.07621 0.07297 -0.0218 0.9992 0.0418 -7.000 -0.5699 0.07321 0.06994 -0.0208 0.9986 0.0426 -6.750 -0.5735 0.07028 0.06695 -0.0189 0.9988 0.0434 -6.500 -0.5773 0.06735 0.06393 -0.0167 0.9993 0.0443 -6.250 -0.5700 0.06364 0.06005 -0.0167 0.9980 0.0461 -6.000 -0.5585 0.06192 0.05745 -0.0164 0.9950 0.0493 -5.750 -0.5514 0.05495 0.05063 -0.0164 0.9945 0.0505 -5.500 -0.5381 0.05212 0.04783 -0.0157 0.9936 0.0516 -5.250 -0.5222 0.04964 0.04528 -0.0152 0.9916 0.0533 -5.000 -0.5029 0.04714 0.04258 -0.0149 0.9892 0.0567 -4.750 -0.4846 0.04404 0.03890 -0.0140 0.9868 0.0621 -4.500 -0.4589 0.04139 0.03628 -0.0152 0.9845 0.0645 -4.250 -0.4382 0.03968 0.03439 -0.0144 0.9813 0.0693 -4.000 -0.4152 0.03719 0.03158 -0.0143 0.9783 0.0766 -3.750 -0.3871 0.03617 0.03016 -0.0146 0.9751 0.0886 -3.500 -0.3630 0.03372 0.02782 -0.0149 0.9713 0.0932 -3.250 -0.3328 0.03216 0.02608 -0.0159 0.9682 0.1079 -3.000 -0.2900 0.02757 0.02031 -0.0133 0.9661 0.0524 -2.750 -0.2585 0.02630 0.01839 -0.0117 0.9631 0.0401 -2.500 -0.2239 0.02462 0.01655 -0.0128 0.9605 0.0405 -2.250 -0.1912 0.02387 0.01567 -0.0134 0.9566 0.0398 -2.000 -0.1550 0.02268 0.01443 -0.0146 0.9514 0.0395 -1.750 -0.1147 0.02176 0.01350 -0.0166 0.9434 0.0401 -1.500 -0.0587 0.02051 0.01236 -0.0217 0.9350 0.0434 -1.250 0.2465 0.01567 0.01074 -0.0750 0.9372 1.0000 -1.000 0.2765 0.01542 0.01038 -0.0753 0.9272 1.0000 -0.750 0.3120 0.01512 0.00997 -0.0764 0.9196 1.0000 -0.500 0.3339 0.01495 0.00973 -0.0750 0.9110 1.0000 -0.250 0.3571 0.01479 0.00951 -0.0738 0.9038 1.0000 0.000 0.3798 0.01455 0.00920 -0.0723 0.8956 1.0000 0.250 0.4001 0.01434 0.00895 -0.0704 0.8865 1.0000 0.500 0.4227 0.01389 0.00846 -0.0683 0.8787 1.0000 0.750 0.4422 0.01365 0.00819 -0.0661 0.8682 1.0000 1.000 0.4625 0.01333 0.00783 -0.0638 0.8588 1.0000 1.250 0.4828 0.01284 0.00729 -0.0611 0.8502 1.0000 1.500 0.5030 0.01252 0.00696 -0.0589 0.8377 1.0000 1.750 0.5236 0.01216 0.00659 -0.0568 0.8237 1.0000 2.000 0.5447 0.01178 0.00620 -0.0548 0.8058 1.0000 2.250 0.5661 0.01157 0.00604 -0.0534 0.7730 1.0000 2.500 0.5846 0.01056 0.00472 -0.0494 0.6748 1.0000 2.750 0.5999 0.01110 0.00425 -0.0460 0.5303 1.0000 3.000 0.6162 0.01219 0.00461 -0.0442 0.4053 1.0000 3.250 0.6336 0.01306 0.00499 -0.0427 0.3330 1.0000 3.500 0.6531 0.01370 0.00535 -0.0415 0.2985 1.0000 3.750 0.6740 0.01419 0.00568 -0.0403 0.2785 1.0000 4.000 0.6956 0.01461 0.00598 -0.0393 0.2651 1.0000 4.250 0.7170 0.01504 0.00629 -0.0383 0.2551 1.0000 4.500 0.7393 0.01539 0.00659 -0.0373 0.2468 1.0000 4.750 0.7610 0.01587 0.00696 -0.0363 0.2406 1.0000 5.000 0.7839 0.01620 0.00731 -0.0354 0.2350 1.0000 5.250 0.8064 0.01660 0.00766 -0.0346 0.2298 1.0000 5.500 0.8292 0.01713 0.00810 -0.0338 0.2249 1.0000 5.750 0.8522 0.01748 0.00852 -0.0330 0.2204 1.0000 6.000 0.8754 0.01790 0.00893 -0.0322 0.2163 1.0000 6.250 0.8988 0.01842 0.00939 -0.0316 0.2121 1.0000 6.500 0.9220 0.01890 0.00992 -0.0309 0.2074 1.0000 6.750 0.9443 0.01927 0.01034 -0.0300 0.2024 1.0000 7.000 0.9672 0.01974 0.01078 -0.0293 0.1978 1.0000 7.250 0.9914 0.02044 0.01146 -0.0289 0.1936 1.0000 7.500 1.0129 0.02079 0.01195 -0.0279 0.1893 1.0000 7.750 1.0345 0.02119 0.01239 -0.0269 0.1843 1.0000 8.000 1.0586 0.02196 0.01306 -0.0266 0.1792 1.0000 8.250 1.0782 0.02229 0.01357 -0.0253 0.1748 1.0000 8.500 1.0985 0.02268 0.01405 -0.0242 0.1700 1.0000 8.750 1.1200 0.02318 0.01453 -0.0234 0.1656 1.0000 9.000 1.1420 0.02393 0.01535 -0.0227 0.1612 1.0000 9.250 1.1605 0.02434 0.01594 -0.0213 0.1570 1.0000 9.500 1.1800 0.02479 0.01646 -0.0201 0.1526 1.0000 9.750 1.2015 0.02545 0.01708 -0.0194 0.1484 1.0000 10.000 1.2176 0.02594 0.01777 -0.0177 0.1439 1.0000 10.250 1.2327 0.02620 0.01817 -0.0158 0.1388 1.0000 10.500 1.2490 0.02652 0.01848 -0.0141 0.1346 1.0000 10.750 1.2647 0.02713 0.01921 -0.0125 0.1304 1.0000 11.000 1.2777 0.02752 0.01979 -0.0103 0.1259 1.0000 11.250 1.2904 0.02781 0.02013 -0.0081 0.1220 1.0000 11.500 1.3008 0.02829 0.02063 -0.0056 0.1180 1.0000 11.750 1.3080 0.02872 0.02127 -0.0026 0.1136 1.0000 12.000 1.3163 0.02911 0.02175 0.0001 0.1097 1.0000 12.250 1.3253 0.02971 0.02236 0.0025 0.1058 1.0000 12.500 1.3344 0.03034 0.02322 0.0047 0.1007 1.0000 12.750 1.3419 0.03095 0.02387 0.0070 0.0960 1.0000 13.000 1.3501 0.03185 0.02492 0.0090 0.0901 1.0000 13.250 1.3550 0.03286 0.02593 0.0111 0.0841 1.0000 13.500 1.3603 0.03415 0.02738 0.0131 0.0767 1.0000 13.750 1.3599 0.03594 0.02920 0.0154 0.0703 1.0000 14.000 1.3593 0.03786 0.03120 0.0175 0.0648 1.0000 14.250 1.3551 0.04025 0.03362 0.0197 0.0609 1.0000 14.500 1.3542 0.04245 0.03598 0.0214 0.0576 1.0000 14.750 1.3515 0.04485 0.03847 0.0228 0.0552 1.0000 15.000 1.3456 0.04768 0.04130 0.0241 0.0533 1.0000 15.250 1.3416 0.05056 0.04433 0.0252 0.0519 1.0000 15.500 1.3374 0.05360 0.04757 0.0257 0.0507 1.0000 15.750 1.3321 0.05690 0.05105 0.0259 0.0496 1.0000 16.000 1.3261 0.06049 0.05479 0.0258 0.0486 1.0000 16.250 1.3195 0.06433 0.05878 0.0252 0.0478 1.0000 16.500 1.3126 0.06837 0.06295 0.0243 0.0470 1.0000 16.750 1.3049 0.07268 0.06738 0.0231 0.0463 1.0000 17.000 1.2972 0.07710 0.07192 0.0217 0.0456 1.0000 17.250 1.2896 0.08153 0.07642 0.0205 0.0449 1.0000 17.500 1.2789 0.08644 0.08142 0.0192 0.0441 1.0000 17.750 1.2610 0.09314 0.08834 0.0158 0.0439 1.0000 18.000 1.2407 0.10052 0.09593 0.0119 0.0437 1.0000 18.250 1.2169 0.10880 0.10441 0.0073 0.0436 1.0000 18.500 1.1891 0.11819 0.11400 0.0020 0.0437 1.0000 18.750 1.1550 0.12933 0.12531 -0.0045 0.0439 1.0000